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-rw-r--r--creator.py101
-rw-r--r--evaluator.py34
-rw-r--r--main.py14
3 files changed, 76 insertions, 73 deletions
diff --git a/creator.py b/creator.py
index a4f67ad..fb6e4e1 100644
--- a/creator.py
+++ b/creator.py
@@ -221,6 +221,56 @@ class Airfoil(Coordinates):
print('z_c the camber z-coordinates:\n', np.around(self.x_u, round))
return None
+ def plot(self):
+ '''This function plots the elements passed as arguments.'''
+
+ # Plot chord
+ x_chord = [0, self.chord]
+ y_chord = [0, 0]
+ plt.plot(x_chord, y_chord, linewidth='1')
+ # Plot quarter chord
+ plt.plot(self.chord / 4, 0, '.', color='g')
+ # Plot mean camber line
+ plt.plot(self.x_c, self.y_c,
+ '-.', color='r', linewidth='2',
+ label='mean camber line')
+ # Plot upper surface
+ plt.plot(self.x_u, self.z_u,
+ '', color='b', linewidth='1')
+ # Plot lower surface
+ plt.plot(self.x_l, self.z_l,
+ '', color='b', linewidth='1')
+
+ # Plot spars
+ for _ in range(0, len(self.spar.x_u)):
+ x = (self.spar.x_u[_], self.spar.x_l[_])
+ y = (self.spar.z_u[_], self.spar.z_l[_])
+ plt.plot(x, y, '.-', color='b')
+
+ # Plot stringers
+ # Upper stringers
+ for _ in range(0, len(self.stringer.x_u)):
+ x = self.stringer.x_u[_]
+ y = self.stringer.z_u[_]
+ plt.plot(x, y, '.', color='y')
+ # Lower stringers
+ for _ in range(0, len(self.stringer.x_l)):
+ x = self.stringer.x_l[_]
+ y = self.stringer.z_l[_]
+ plt.plot(x, y, '.', color='y')
+
+ # Graph formatting
+ plt.xlabel('X axis')
+ plt.ylabel('Z axis')
+
+ plot_bound = self.x_u[-1]
+ plt.xlim(- 0.10 * plot_bound, 1.10 * plot_bound)
+ plt.ylim(- (1.10 * plot_bound / 2), (1.10 * plot_bound / 2))
+ plt.gca().set_aspect('equal', adjustable='box')
+ plt.grid(axis='both', linestyle=':', linewidth=1)
+ plt.show()
+ return None
+
class Spar(Coordinates):
'''Contains a single spar's location.'''
@@ -359,57 +409,6 @@ class Stringer(Coordinates):
return None
-def plot(airfoil, spar, stringer):
- '''This function plots the elements passed as arguments.'''
-
- # Plot chord
- x_chord = [0, airfoil.chord]
- y_chord = [0, 0]
- plt.plot(x_chord, y_chord, linewidth='1')
- # Plot quarter chord
- plt.plot(airfoil.chord / 4, 0, '.', color='g')
- # Plot mean camber line
- plt.plot(airfoil.x_c, airfoil.y_c,
- '-.', color='r', linewidth='2',
- label='mean camber line')
- # Plot upper surface
- plt.plot(airfoil.x_u, airfoil.z_u,
- '', color='b', linewidth='1')
- # Plot lower surface
- plt.plot(airfoil.x_l, airfoil.z_l,
- '', color='b', linewidth='1')
-
- # Plot spars
- for _ in range(0, len(spar.x_u)):
- x = (spar.x_u[_], spar.x_l[_])
- y = (spar.z_u[_], spar.z_l[_])
- plt.plot(x, y, '.-', color='b')
-
- # Plot stringers
- # Upper stringers
- for _ in range(0, len(stringer.x_u)):
- x = stringer.x_u[_]
- y = stringer.z_u[_]
- plt.plot(x, y, '.', color='y')
- # Lower stringers
- for _ in range(0, len(stringer.x_l)):
- x = stringer.x_l[_]
- y = stringer.z_l[_]
- plt.plot(x, y, '.', color='y')
-
- # Graph formatting
- plt.xlabel('X axis')
- plt.ylabel('Z axis')
-
- plot_bound = airfoil.x_u[-1]
- plt.xlim(- 0.10 * plot_bound, 1.10 * plot_bound)
- plt.ylim(- (1.10 * plot_bound / 2), (1.10 * plot_bound / 2))
- plt.gca().set_aspect('equal', adjustable='box')
- plt.grid(axis='both', linestyle=':', linewidth=1)
- plt.show()
- return None
-
-
def main():
return None
diff --git a/evaluator.py b/evaluator.py
index 59d233a..489b346 100644
--- a/evaluator.py
+++ b/evaluator.py
@@ -20,16 +20,19 @@ import numpy as np
from math import sin, cos, atan, sqrt
-class Evaluator:
+class Airfoil:
'''Performs structural evaluations for the airfoil passed as argument.'''
def __init__(self, airfoil):
self.airfoil = airfoil
+ print(self.airfoil)
# Global dimensions
self.chord = airfoil.chord
self.semi_span = airfoil.semi_span
# mass and area
- self.mass_total = airfoil.mass + airfoil.spar.mass + airfoil.stringer.mass
+ self.mass_total = float(airfoil.mass
+ + airfoil.spar.mass
+ + airfoil.stringer.mass)
self.mass_dist = []
self.lift_rectangular = []
@@ -51,6 +54,7 @@ class Evaluator:
print('Chord length:', self.chord)
print('Semi-span:', self.semi_span)
print('Total airfoil mass:', self.mass_total)
+ print('Centroid location:', np.around(self.centroid, round + 1))
print(22 * '-')
print('Rectangular lift:\n', np.around(self.lift_rectangular, round))
print('Elliptical lift:\n', np.around(self.lift_elliptical, round))
@@ -114,10 +118,19 @@ class Evaluator:
F_x.extend([1.25 * drag for x in semi_span[cutoff:]])
return F_x
+ def get_centroid(self):
+ area = self.airfoil.stringer.area
+ x_stringers = self.airfoil.stringer.x_u + self.airfoil.stringer.x_l
+ x_centroid = sum([x * area for x in x_stringers]) / \
+ (len(x_stringers) * area)
+
+ z_stringers = self.airfoil.stringer.z_u + self.airfoil.stringer.z_l
+ z_centroid = sum([x * area for x in z_stringers]) / \
+ (len(x_stringers) * area)
+ return(x_centroid, z_centroid)
+
def analysis(self):
- '''
- Perform all analysis calculations and store in class instance.
- '''
+ '''Perform all analysis calculations and store in class instance.'''
self.drag = self.get_drag(10)
@@ -125,18 +138,9 @@ class Evaluator:
self.lift_elliptical = self.get_lift_elliptical(15)
self.lift = self.get_lift_total()
- # self.mass_total = self.get_mass_total()
self.mass_dist = self.get_mass_distribution(self.mass_total)
+ self.centroid = self.get_centroid()
return None
-# def get_centroid(airfoil):
-# area = airfoil.stringer.area
-# top_stringers = airfoil.stringer
-# bottom_stringers =
-# nose_top_stringers =
-# nose_bottom_stringers =
-# for _ in airfoil.stringer[1]:
-# centroid.x +=
-
# denominator
# z_c =
diff --git a/main.py b/main.py
index 821bbb6..6d9fa9a 100644
--- a/main.py
+++ b/main.py
@@ -23,8 +23,8 @@ start_time = time.time()
# Airfoil dimensions
NACA_NUM = 2412
-CHORD_LENGTH = 40
-SEMI_SPAN = 200
+CHORD_LENGTH = 20
+SEMI_SPAN = 20
# Component masses
AIRFOIL_MASS = 10 # lbs
@@ -77,15 +77,15 @@ def main():
# af.stringer.print_info(2)
# Plot components with matplotlib
- # creator.plot(af, af.spar, af.stringer)
+ af.plot()
# Save component info
- af.save_info(SAVE_PATH, _)
- af.spar.save_info(SAVE_PATH, _)
- af.stringer.save_info(SAVE_PATH, _)
+ # af.save_info(SAVE_PATH, _)
+ # af.spar.save_info(SAVE_PATH, _)
+ # af.stringer.save_info(SAVE_PATH, _)
# evaluator.Evaluator instance contains airfoil analysis results.
- eval = evaluator.Evaluator(af)
+ eval = evaluator.Airfoil(af)
# The analysis is performed in the evaluator.py module.
eval.analysis()
eval.print_info(2)
Copyright 2019--2024 Marius PETER